Split fuel control module

ABSTRACT

A split fuel control module for a gas turbine engine and method of installation. The split fuel control module includes a first frame unit, a second frame unit, a segmented fuel path, and a distributed fuel controller. The first frame unit and the second frame unit are joined together at a frame unit interface. The segmented fuel path includes an upstream fuel interface fixed to the first frame unit and a downstream fuel interface fixed to the second frame unit and detachably coupled to the upstream fuel interface at the frame unit interface. A first portion of the distributed fuel controller is fixed to the first frame unit, and a second portion of the distributed fuel controller is fixed to the second frame unit.

TECHNICAL FIELD

The present disclosure generally pertains to gas turbine engines, and ismore particularly directed toward a fuel control module for a gasturbine engine.

BACKGROUND

Stationary gas turbine engines are typically assembled into a “gasturbine engine package”. In particular, the gas turbine engine andcertain support systems are installed on or within an enclosure on asupport platform, keeping systems necessary to the turbine's operationtogether and in proximity. In some instances, certain support systemsmay be assembled during the build up of the support platform, before theactual installation of the gas turbine engine. In this way the supportsystems may be easily “dropped in” the support platform with minimalinterference, and connected up to the gas turbine engine after it isinstalled.

U.S. Pat. App. Pub. No. 2010/0162726 Robertson et al. published on Jul.1, 2010 shows a mobile platform system for a gas turbine engine. Inparticular, the disclosure of Robertson et al. is directed toward asystem for moving an auxiliary component of a gas turbine engine. Thesystem may have a mobile support platform configured to support theauxiliary component during operation of the gas turbine engine. Thesystem may further have at least one guide assembly operably connectedto the mobile support platform and configured to guide movement of themobile support platform. The system may also have a drive assemblyoperably connected to the mobile support platform and configured toimpart movement of the mobile support platform between an elevatedposition and a lowered position.

The present disclosure is directed toward overcoming known problemsand/or problems discovered by the inventors.

SUMMARY OF THE DISCLOSURE

A split fuel control module for a gas turbine engine is disclosedherein. The split fuel control module includes a first frame unit, asecond frame unit, a segmented fuel path, and a distributed fuelcontroller. The first and second frame units each include a base and aninner side joined together at substantially a right angle, respectively.The first and second frame units are joined together at a frame unitinterface. The segmented fuel path includes a fuel inlet, a fuel outlet,an upstream fuel interface fixed to the first frame unit, and adownstream fuel interface fixed to the second frame unit and detachablycoupled to the upstream fuel interface at the frame unit interface. Thedistributed fuel controller includes a primary fuel shut-off valve and amain fuel control valve. A first portion of the distributed fuelcontroller is fixed to the first frame unit, and a second portion of thedistributed fuel controller is fixed to the second frame unit. Accordingto one embodiment, a gas turbine engine package is also disclosedherein. The gas turbine engine package includes a gas turbine engine, asupport platform, and the above split fuel control module fluidlycoupled to the gas turbine engine, and mounted to the support platform.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a cutaway isometric view of a gas turbine engine package.

FIG. 2 is an isometric view of the exemplary split fuel control moduleof FIG. 1.

FIG. 3 is a partial side view of the split fuel control module of FIG.2.

FIG. 4 is a partial top view of a support platform of the gas turbineengine package of FIG. 1, including a base plate for the split fuelcontrol module of FIG. 2.

FIG. 5 is a top view of the split fuel control module of FIG. 2.

FIG. 6 is a flow chart of an exemplary method for installing a splitfuel control module.

DETAILED DESCRIPTION

The split fuel control module is a fuel control module for a gas turbineengine that is divided into individual frame units for installation, andassembled into a single frame module for operation. Each individualframe unit includes independent transport features and a coordinatedframe unit interface for subsequent assembly. An individual unitincludes a portion of the fuel train and is configured to be installedwithout the need to remove the gas turbine engine.

FIG. 1 is a cutaway isometric view of a gas turbine engine package. Someof the surfaces have been left out or exaggerated (here and in otherfigures) for clarity and ease of explanation. In FIG. 1, some of theenclosure 102 has been cut away to show some the interior components.

The gas turbine engine package 100 may include a gas turbine engine 101,an enclosure 102, and a support platform 103. The gas turbine engine 101may be mounted to and supported by the support platform 103. Inaddition, the gas turbine engine 101 may be housed in the enclosure 102.The gas turbine engine package 100 may also include one or moreauxiliary features such as an inlet duct 104, an exhaust duct 105, oneor more vents 106, and a control panel 107, for example.

Generally, the gas turbine engine 101 includes an inlet, a compressor, acombustor, a turbine, an exhaust, and a power output coupling. One ormore of the gas turbine engine's 101 rotating components are coupledtogether by one or more rotating shafts.

Functionally, air enters the gas turbine engine inlet via the inlet duct104 and is compressed by the compressor. Once compressed, the air leavesthe compressor, and enters the combustor, where it is diffused and fuelis added. In particular, fuel is supplied to a plurality of fuelinjectors from a fuel supply and via a fuel control module (here, splitfuel control module 700). The split fuel control module 700 is locatedoff of the gas turbine engine 101, but within the gas turbine enginepackage 100, and is fluidly coupled to the plurality of fuel injectors.After the combustion reaction, energy is then extracted from thecombusted fuel/air mixture via the turbine. Exhaust gas then exits thesystem via the exhaust duct 105.

Various types of gaseous and liquid fuels may be directed into thecombustor through fuel injectors. The gaseous fuel may include, forexample, natural gas, landfill gas, bio-gas, syngas, etc. The liquidfuels may include diesel, kerosene, gasoline, or any other type ofliquid fuel. In some applications, the gas turbine engine 101 may beoperated primarily using a fuel that is cheaply available at thelocation where the gas turbine engine 101 is operating. For example, inan oil field with an abundant supply of natural gas, the gas turbineengine 101 may operate primarily using natural gas. In suchapplications, liquid fuel may be reserved for engine operatingconditions where a liquid fuel may be more desirable. For instance, aliquid fuel may be directed to gas turbine engine 101 during startup andwhen combustion instabilities are detected in the combustor. After thegas turbine engine 101 reaches a stable operating condition, the liquidfuel supply to the gas turbine engine 101 may be turned off, and thegaseous fuel supply turned on.

FIG. 2 is an isometric view of the exemplary split fuel control moduleof FIG. 1. In particular, the split fuel control module 700 is shown asa stand-alone structure having the functional components to control fuelflow to the injectors of a gas turbine engine. Some of the surfaces andplumbing have been left out or exaggerated for clarity and ease ofexplanation.

As illustrated, the split fuel control module 700 includes two frameunits 701, a segmented fuel path 710, and a distributed fuel controller750. The distributed fuel controller 750 generally includes the assortedcontrollers and devices that interface with the segmented fuel path 710,which includes the assorted interfaces and passageways that carry anddistribute fuel through the split fuel control module 700.

The split fuel control module 700 may further include a segmented airpath 720, one or more terminal boxes 730, one or more transmitters 740,and other componentry. As above, the segmented fuel path 710 generallyincludes the assorted interfaces and passageways that carry anddistribute air or gas through the split fuel control module 700.According to one embodiment the split fuel control module 700 mayinclude more than two frame units 701.

Each frame unit 701 supports a portion of the segmented fuel path 710, aportion of the segmented air path 720, and/or a portion of thedistributed fuel controller 750. According to one embodiment, the splitfuel control module 700 may include more than two frame units 701, eachsupporting a portion of the segmented fuel path 710, a portion of thesegmented air path 720, and/or a portion of the distributed fuelcontroller 750.

Each frame unit 701 is joined together at a frame unit interface 791 toform the split fuel control module 700. According to one embodiment, theframe unit interface 791 may be a reference plane. According to anotherembodiment, the frame unit interface 791 may be a reference complexsurface. In addition, segments of the segmented fuel path 710 arefluidly coupled together at the frame unit interface 791. Similarly,segments of the segmented air path 720 are fluidly coupled together atthe frame unit interface 791.

Each frame unit 701 includes a base 703 and an inner side 704. The frameunit 701 may also include an outer side 705 located opposite the base703 from the inner side 704. According to one embodiment, the inner side704 and the outer side 705 may be joined to opposite ends of the base703 and extend in the same direction, perpendicularly from the base 703,perpendicular meaning exactly perpendicular plus or minus five degreesin either direction. According to one embodiment, the base 703 may havea rectangular footprint and have a centerline 702 (FIG. 5) runningbetween the inner side 704 and the outer side 705. According to oneembodiment, the footprint of each frame unit 701 is limited not toexceed a vertical channel where the base 703 may be freely loweredalongside the gas turbine engine 101 to the support platform 103(FIG. 1) without lateral contact.

The structural members forming each frame unit 701 are coupled together.In particular, the inner side 704 and the outer side 705 may be joinedto the base 703 using fasteners, welded together, using locking joints,and/or using any conventional joining. According to one embodiment, thebase 703, the inner side 704, and the outer side 705 may be formed froma single material.

The frame unit 701 may include at least one side support 706. Each sidesupport 706 may be joined to the base 703 and to the inner side 704and/or the outer side 705. Each side support 706 and may be configuredstructurally as a corner brace. In particular, each side support 706 maybe configured to strengthen the frame unit 701 against loading on thejoint between the base 703 and the inner side 704, and/or between thebase 703 and the outer side 705.

According to one embodiment, the frame unit 701 may include four sidesupports 706, for example, where the base 703 is rectangular, one may belocated at each corner between the base 703 and the inner side 704 andthe outer side 705. Additionally, each side support 706 may couple tothe base 703, and to the inner side 704 or the outer side 705, extendingperpendicularly from the base 703. According to another embodiment, theframe unit 701 may include two side supports 706 extending the length ofthe base between the inner side 704 and the outer side 705. For example,where the base 703 is rectangular, each side support 706 may be coupledto and extend orthogonally from the first base 703, the first inner side704, and the first outer side 705, orthogonal meaning exactly orthogonalplus or minus five degrees in any direction.

The structural members of the frame unit 701 may be made of corrosionresistant steel or any other suitable structural material. In addition,the structural members may be lightened by removing material and/orcreating holes throughout the frame unit 701. According to oneembodiment, material may be removed from the structural members to formfunctional features of the frame unit 701, as discussed further below.

The frame unit 701 includes transport features. In particular, the frameunit 701 may include a plurality of lifting devices 707 that couple witha mating transport device off of the frame unit 701, such as on a craneor other lifting machinery. For example, a lifting device 707 mayinclude integrated features (e.g., openings, notches, hook arms, etc.)or added-on attachments (e.g., brackets, rings, hooks, etc.) that cancouple with a crane attachment (e.g., hook, cable, rope, etc.) or thelike. In this way, the frame unit 701 may be lifted, carried and loweredinto position for assembly.

According to one embodiment, a lifting device 707 may include a sectionof the inner side 704 and/or a section of the outer side 705 configuredto receive the crane attachment. In particular, the inner side 704and/or the outer side 705 may include integrated features or added-onattachments. For example, as illustrated, lifting device 707 may includea plurality of openings in an upper portion of the inner side 704 and/orthe outer side 705. The openings are perforations through the inner side704 and/or the outer side 705. The plurality of openings may be round(as illustrated), or of any convenient shape. Moreover, as discussedabove, plurality of openings may be oversized so as to incrementallyreduce the weight of the frame unit 701, and thus make it moremaneuverable.

According to one embodiment, the lifting devices 707 may includemultiple lift configurations. In particular, the lifting devices 707 mayincorporate balanced and/or off-balanced lift points. Moreover, thelifting devices 707 may incorporate symmetric and/or asymmetric liftpoints. For example, where the plurality of lifting devices 707 is madeup plurality of openings in an upper portion of the inner side 704 andthe outer side 705, four openings (two on the inner side 704 and two onthe outer side 705) may be positioned such that, when the frame unit 701is lifted, the base 703 is balanced and remains substantiallyhorizontal. Alternately, the four openings may be located such that,when the frame unit 701 is lifted, the base 703 is imbalanced and tiltsat a non-horizontal angle.

Moreover, the plurality of lifting devices 707 may include bothembodiments combined (i.e., balanced and imbalanced), to include six ormore openings such that the frame unit 701 may be hoisted with the base703 remaining substantially horizontal, or at one or more non-horizontalangles, depending on which combination of openings of the lifting device707 are coupled to the lifting machine, and on the weigh distribution onthe base 703. The one or more non-horizontal angles may be set tocoincide with a desired entry angle. For instance, an angled entry maybe selected to avoid contact with the gas turbine engine 101 (FIG. 1),or for subsequent maneuvering and/or alignment after an initial landing.

Also for example, the plurality of lifting devices 707 may be symmetricwith each other. In particular, the plurality of lifting devices 707 mayinclude two openings on the inner side 704 and two openings on the outerside 705, all four located perpendicularly equidistant from the base 703and perpendicularly equidistant from the centerline 702 (FIG. 5) of thebase 703. In addition, each opening may be located between one diameterand two diameters from opposite edges of the inner side 704 and theouter side 705, respectively. Here, a “diameter” may include the maximumdimension of the respective opening in the direction perpendicular fromthe centerline 702. Also, the location of an opening may be measured atits center, at an edge, and/or consistently at any convenient pointwithin.

Alternately, the plurality of lifting devices 707 may be non-symmetricwith another. In particular, at least one opening on the inner side 704or on the outer side 705 may be located at a perpendicular distance fromthe base 703 and/or perpendicular distance from the centerline 702 (FIG.5) of the base 703 different from at least one other opening. Toillustrate, a first opening on the inner side 704 and a first opening onthe outer side 705 may be located perpendicularly equidistant from thebase 703 and perpendicularly equidistant from the centerline 702 of thebase 703, whereas a second opening on the inner side 704 and a secondopening on the outer side 705 may be located, relative to each other,perpendicularly equidistant from the base 703 and perpendicularlyequidistant from the centerline 702 of the base 703, but at a differentperpendicular distance from the base 703 or perpendicular distance fromthe centerline 702 of the base 703 than the first openings.

Moreover, the plurality of lifting devices 707 may include bothembodiments combined (i.e., symmetric and non-symmetric). In particular,the frame unit 701 may include six or more openings located at bothsymmetric and asymmetric locations such that the frame unit 701 may behoisted at symmetrical or asymmetrical attach points, depending on whichcombination of openings of the lifting device 707 are selected. Also,depending on the weigh distribution on the base 703, selection ofasymmetric openings may provide for a balanced lift, an imbalanced lift,or a tilted lift. Likewise, depending on the weigh distribution on thebase 703, selection of symmetric openings may provide for a balancedlift, an imbalanced lift, or a tilted lift.

According to one embodiment, the plurality of lifting devices 707 may beconfigured for universal installation. In particular, using thedisclosed plurality of lifting devices 707, the split fuel controlmodule 700 may be installed in multiple installations and/or multipleconfigurations. Here, multiple installations may include multiple gasturbine engine packages 100. Similarly, multiple configurations mayinclude variations in the positioning or orientation of the split fuelcontrol module 700 within a single gas turbine engine package 100,and/or variations in the positioning or orientation of the individualframe units 701 within the gas turbine engine package 100. For example,the frame unit 701 may include additional lifting devices 707 for themultiple installations and/or multiple configurations. To illustrate,the frame unit 701 may include lifting devices 707 configured formultiple entry angles associated with different gas turbine enginepackages 100. Alternately, the frame unit 701 may include liftingdevices 707 configured for both a left hand and a right hand entry.Alternately, the frame unit 701 may include lifting devices 707configured for the split fuel control module 700 to be installed forwardfacing or rearward facing (i.e., with the centerlines 702 of the bases703 rotated 180 degrees).

According to one embodiment the plurality of lifting devices 707 may bepositioned relative to the vertical weight distribution of the frameunit 701 when the base 703 is resting on a horizontal surface. Inparticular, the plurality of lifting devices 707 may be positioned abovethe center of gravity of the frame unit 701. For example, the inner side704 and the outer side 705 may sufficiently extend vertically beyond thecenter of gravity, and the lifting devices 707 may be located at the topof the inner side 704 and the outer side 705, respectively. According toone embodiment, each opening may be between one diameter and twodiameters from the tops of the inner side 704 and the outer side 705,respectively. Here, a “diameter” may include the maximum dimension ofthe respective opening in the vertical direction.

The fuel inlet 711 is an interface to couple with a fuel conduit toreceive fuel from a fuel supply. In particular, the fuel inlet 711 maybe any conventional fitting mating with the fuel supply. For example,the fuel inlet 711 may include a ¾″ 150 LB ANSI RF flange. Also forexample, the fuel inlet 711 may include a metric flange, or anyconventional coupling meeting the particular specifications of thefacility where the gas turbine engine 101 (FIG. 1) is located, and ofthe fuel system of the gas turbine engine 101. The fuel conduit mayinclude any conventional fuel plumbing and intervening structures.

FIG. 3 is a partial side view of the split fuel control module of FIG.2. In particular, two populated frame units 701 are shown separatedapart at the frame unit interface 791.

The frame unit 701 may include an interface alignment guide 708. Inparticular, each frame unit 701 may include a fixed or removableinterface alignment guide 708 configured to control movement andalignment over a range when two frame units 701 are joined together. Theinterface alignment guide 708 aligns the two frame units 701 withsufficient precision to maintain any required interface tolerances.

According to one embodiment, the interface alignment guide 708 mayinclude two taper pins (with mating receptacles on the other frame unit701). The taper pin may be made of a high strength material such as AISI4340 steel, for example. The taper pin may have a diameter approximately0.70″ (1.78 cm), and extend from the inner side 704 of one frame units701 for a length of approximately 4″ (10.16 cm). The taper pin may taperapproximately 0.25″ diameter per foot of length (0.64 cm dia./31.5 cmlen.). The taper pin may have a greater or lesser diameter, length,and/or taper as well.

Each taper pin may be located on opposite sides of centerline 702 (FIG.5). Also, both taper pins may be located on the inner side 704 of oneframe unit 701, with the mating receptacles on the inner side 704 of theother frame unit 701. Alternately, the taper pins may alternate, withone taper pin and one mating receptacle located on the inner side 704 ofone frame unit 701, and with the other mating receptacle and the othertaper pin located on the inner side 704 of the other frame unit 701.

The frame unit 701 may also include a mechanism for drawing two frameunits 701 together such as a frame puller 709. In particular, each frameunit 701 may include a frame puller 709 configured to draw together andcouple a first frame unit 701 and the second frame unit 701 over arange. Together the interface alignment guide 708 and the frame puller709 may be used to draw two frame units 701 together in a guided mannerfor final assembly of the split fuel control module. For example, oncethe frame units 701 are in sufficient proximity, the frame puller 709may engage, in conjunction with the interface alignment guide 708, andbe used to draw each other together over the range until reaching theirinterface tolerances.

According to one embodiment, the frame puller 709 may include twothreaded shafts and nuts. The threaded shaft and nut may be made of ahigh strength material such as AISI 4340 steel, for example. Thethreaded shaft may have a diameter approximately 0.70″ (1.78 cm), andextend from the inner side 704 of one frame units 701 for a length ofapproximately 4″ (10.16 cm). The threaded shaft may have a greater orlesser diameter and/or length as well, depending on the pulling forcesand range required. Additional hardware such as washers, backing plates,etc. are contemplated.

Additionally and similar to the taper pins, the threaded shafts may belocated on opposite sides of centerline 702 (FIG. 5). Also, boththreaded shafts may be located on the inner side 704 of one frame unit701, with mating receptacles on the inner side 704 of the other frameunit 701. Alternately, the threaded studs may alternate, with onethreaded stud and one mating receptacle may be located on the inner side704 of one frame unit 701, and with the other mating receptacle and theother threaded stud located on the inner side 704 of the other frameunit 701.

The upstream fuel interface 712 and the downstream fuel interface 713(FIG. 3) are mating fittings that complete the fuel path across theframe unit interface 791. The upstream fuel interface 712 and thedownstream fuel interface 713 are configured to be fluidly coupled oncea first frame unit 701 and a second frame unit 701 are drawn togetherand coupled via the frame puller 709 (FIG. 3). According to oneembodiment the upstream fuel interface 712 and the downstream fuelinterface 713 may be mating flanges and may include an “O” ring or otherseal therebetween.

According to one embodiment, the fuel inlet 711 may be recessed withinframe unit 701, such that the segmented fuel path 710 may receive fuelfrom various supply interfaces. In particular, the fuel inlet 711 may berecessed inboard from the outer side 705 such that a bend, such as aninety-degree coupling, may reside substantially within the frame unit701 while turning. For example, the fuel inlet 711 may be recessed atleast 7″ (17.8 cm) inboard of the outer side 705. Also for example, thefuel inlet 711 may be recessed between 6″ and 12″ (15.2 cm-30.5 cm)inboard of the outer side 705. Also for example, the fuel inlet 711 maybe recessed between inboard of the outer side 705. Also for example, thefuel inlet 711 may be recessed inboard of the outer side 705 at leastthe distance of diameter of the fuel inlet 711.

FIG. 4 is a partial top view of a support platform of the gas turbineengine package of FIG. 1, including a base plate for the split fuelcontrol module of FIG. 2. In particular, a base plate 792 is shownmounted to and supported by the support platform 103. Furthermore, thebase plate 792 is shown with the split fuel control module 700 (FIG. 2)uninstalled. In this view, both the gas turbine engine 101 and theenclosure 102 (FIG. 1) are removed for clarity.

The base plate 792 is a structural member configured to support aplurality of frame units 701 (FIG. 2). In particular, the base plate 792mounts to the support platform 103 of the gas turbine engine package 100and interfaces with the first and second frame units 701. Furthermore,the base plate 792 forms a single base between the bases 703 of firstand second frame units 701, uniting them as a single unit. The baseplate 792 may be made of plate steel, or any other structural material.

The base plate 792 includes a plurality of interface features. Inparticular, the base plate 792 includes attachment holes 793 for thesupport platform 103, attachment holes 793 for both frame units 701, andaccess holes 794. For example, the attachment holes 793 may be holesmachined in the base plate 792 configured to receive fasteners. Whenassembled, the fasteners may join the base plate 792 to the supportplatform 103 and to both of the frame units 701. The fasteners may beany conventional fastener (e.g., bolts, screws, pins, etc.).

The access holes 794 may include cut outs of any convenient shape, size,and position to provide access to the frame units 701 (FIG. 2). Forexample, the access holes 794 may be positioned to provide sufficientclearance for a technician to reach in and couple the fasteners to thebase plate 792 (e.g., positioned proximate the attachment holes 793), toprovide access for a function of a component of the frame units 701(e.g., drains), or for any other access need. In addition, the accessholes 794 may be oversized beyond their functional requirements in orderto reduce overall weight and/or material costs.

According to one embodiment, the base plate 792 may be configured foruniversal installation. In particular, using the disclosed base plate792, the split fuel control module 700 may be configured to be installedin multiple installations and/or multiple configurations. Here, multipleinstallations may include multiple gas turbine engine packages 100,where there are variations in the installation of the base plate 792and/or variations that include attaching one or more additional supportbrackets 795 to the base plate 792 with one or more installationpositions. Similarly, multiple configurations may include variations inthe positioning or orientation of the base plate 792 within a single gasturbine engine package 100, and/or variations in the positioning ororientation of the frame units 701 on top of the base plate 792.

For example, the attachment holes 793 may include additional holes forthe multiple installations and/or multiple configurations. Alternately,the attachment holes 793 may be slotted, or otherwise providing forvariable attach points, for the multiple installations and/or multipleconfigurations. Also for example, the access holes 794 may includeadditional or duplicate openings for the multiple installations and/ormultiple configurations. Alternately, the access holes 794 may beshaped, enlarged, and/or positioned for the multiple installationsand/or multiple configurations.

FIG. 5 is a top view of the split fuel control module of FIG. 2. Inparticular, two populated frame units 701 are shown installed into thegas turbine engine package 100, mounted to the support platform 103 viathe base plate 792. In this view, both the gas turbine engine 101 andthe enclosure 102 (FIG. 1) are removed for clarity. Each frame unit 701is populated with its respective functional components, and is coupledto the other at the frame unit interface 791, together making the splitfuel control module 700.

Each frame unit 701 supports a portion of the segmented fuel path 710and a portion of the distributed fuel controller 750. Each frame unit701 may further support a portion of the segmented air path 720, aterminal box 730, one or more transmitters 740, and other componentry.

The segmented fuel path 710 is a fuel flow path between a fuel supplyand the fuel system of the gas turbine engine 101 (FIG. 1), andsegmented across the frame unit interface 791. In particular, thesegmented fuel path 710 includes a fuel inlet 711 (FIG. 2), an upstreamfuel interface 712 (FIG. 3), a downstream fuel interface 713 (FIG. 3), afuel outlet 714, and any suitable fluid conduit, piping, ducting,manifolds, etc. therebetween, including passageways though the variousfluid components. The segmented fuel path 710, once assembled, isconfigured to deliver fuel received at from the fuel inlet 711 to thegas turbine engine 101 via the fuel outlet 714.

When the first frame unit 701 and the second frame unit 701 are drawntogether and coupled, the upstream fuel interface 712 and the downstreamfuel interface 713 may be within coupling tolerance. In particular, theframe puller 709 may be used to draw the upstream fuel interface 712 andthe downstream fuel interface 713 precisely within coupling tolerance.For example when coupled via interface alignment guide 708 and the framepuller 709, the upstream fuel interface 712 and the downstream fuelinterface 713 may be approximately centered and axially within 0.025″(0.64 cm) at the frame unit interface 791. Also for example, whencoupled via interface alignment guide 708 and the frame puller 709, theupstream fuel interface 712 and the downstream fuel interface 713 may beapproximately centered and axially between 0.015″ (0.038 cm) and 0.020″(0.051 cm) at the frame unit interface 791.

The fuel outlet 714 is an interface configured to couple with a fuelconduit to deliver fuel to the fuel system of the gas turbine engine 101(FIG. 1). In particular, the fuel outlet 714 is a fuel coupling thatoutputs pressurized and regulated fuel from the split fuel controlmodule 700. For example, the fuel outlet 714 may include a ½″ 150 LBANSI RF flange. Also for example, the fuel outlet 714 may include ametric flange, or any other coupling meeting the particularspecifications of the fuel system. According to one embodiment, the fueloutlet 714 may include a plurality of outlet lines. For example the fueloutlet 714 may include multiple interfaces with the fuel system of thegas turbine engine 101, including an outlet lines plumbed to andassociated with the each fuel control valve of the distributed fuelcontroller 750 (e.g., a main fuel control valve 753, a pilot fuelcontrol valve 754, and a torch fuel control valve).

According to one embodiment, the segmented fuel path 710 may minimizethe couplings between the first and the second frame units 701. Inparticular, the segmented fuel path 710 may cross the frame unitinterface 791 a single time. For example, where the fuel outlet 714includes multiple interfaces with the fuel system of the gas turbineengine 101, the segmented fuel path 710 may include a single fuel pathat the frame unit interface 791, and a manifold 715 that divides thesingle path of the segmented fuel path 710 into a plurality of flowsdownstream of the frame unit interface 791. For example, here, themanifold 715 (also see, FIG. 2) divides the segmented fuel path 710 intotwo flows, one going to a main fuel control valve 753, and one going toa pilot fuel control valve 754.

According to one embodiment, the segmented fuel path 710 may beconfigured for universal installation. In particular, using thedisclosed segmented fuel path 710, the split fuel control module 700 maybe configured to be installed with a plurality of gas turbine enginepackages 100 (FIG. 1), in a plurality of positions on a gas turbineengine package 100, and/or having a plurality of external interfaces.For example, the fuel inlet 711 (FIG. 3) may be aligned with thecenterline 702 of the base 703, such that the segmented fuel path 710may receive fuel equally from either side. Additionally the upstreamfuel interface 712 and the downstream fuel interface 713 (FIG. 3) may bealigned with the centerline 702 of the base 703 (FIG. 2), such thatthere is equal access to assemble the segmented fuel path 710 fromeither side and such that different manifolds 715 may be used (e.g.,where a different number of fuel outlets 714 are present). Additionallyone or more fuel outlets 714 (FIG. 3) may be aligned with the centerline702 of the base 703 such that the segmented fuel path 710 may deliverfuel equally from either side.

The distributed fuel controller 750, which generally includes theassorted controllers and devices that interface with the segmented fuelpath 710, controls and regulates fuel flow into the gas turbine engine101 (FIG. 1). In particular, the distributed fuel controller 750 may beconfigured to provide fuel shutoff, pressure regulation, and/or flowregulation. The distributed fuel controller 750 includes a primary fuelshut-off valve 751, a main fuel control valve 753, and a pressureregulator. The primary fuel shut-off valve 751 may be located in anupstream portion of the segmented fuel path 710, and is configured tostop fuel flow within the segmented fuel path 710 when commanded. Themain fuel control valve 753 is a metering flow valve that controls themain fuel powering the gas turbine engine 101. The pressure regulatormay be integrated into the main fuel control valve 753, providing fuelto the gas turbine engine's main fuel system metered at both therequired flow and pressure.

The distributed fuel controller 750 may further include a secondary fuelshut-off valve 752, a pilot fuel control valve 754, and a torch fuelcontrol valve (not shown). The secondary fuel shut-off valve 752 is aredundant or “back up” shut-off valve, relative to the primary fuelshut-off valve 751, and is configured to stop fuel flow within thesegmented fuel path 710 when commanded. The secondary fuel shut-offvalve 752 may also be located in an upstream portion of the segmentedfuel path 710. The pilot fuel control valve 754 and the torch fuelcontrol valve may be configured to provide fuel metering control forindependent fuel supplies to the gas turbine engine 101 (FIG. 1). Forexample, the pilot fuel system and the ignition torch may requireindependent flow rates, finer metering control, and/or independentinterfaces with the fuel system of the gas turbine engine 101.

According to one embodiment, one or more fluid components of thedistributed fuel controller 750 may be pneumatically activated orpowered. In particular, at least one of the primary fuel shut-off valve751, the secondary fuel shut-off valve 752, the main fuel control valve753, the pilot fuel control valve 754, and the torch fuel control valvemay be air-powered or air-assisted. As such, the air-powered orair-assisted component may also include an interface to the segmentedair path 720.

The segmented air path 720 is an “instrument gas” system within thesplit fuel control module 700, segmented across the frame unit interface791. “Instrument gas” is air or other gas that is clean, filtered, andpressurized. The instrument gas is typically supplied by the facilitywhere the gas turbine engine package 100 is installed. The segmented airpath 720 may include an air inlet 721, an upstream air interface 722(FIG. 3), a downstream air interface 723 (FIG. 3), a supply outlet 724(FIG. 4), a gas vent, and any suitable fluid conduit, piping, air lines,manifolds, etc., therebetween.

According to one embodiment, the split fuel control module 700 may alsobe configured independently ensure air quality and/or provide redundantprotection. In particular, the segmented air path 720 may include itsown air filter 725 (FIG. 3), which is independent and in addition to anyexternal filter of the air supply. The air filter 725 may be embodied asan assembly and configured to clean air received at the air inlet 721prior to being delivered to any supply outlet 724 (FIG. 4). For example,the air filter 725 maybe located downstream but proximate the air inlet721. Additionally, the air filter 725 may be mounted directly to theframe unit 701. For example, as illustrated, the air filter 725 may bemounted to the outer side 705 (FIG. 3) and support the air inlet 721.

Once coupled, the segmented air path 720 is configured to deliverinstrument gas received at the air inlet 721 to one or more fluidcomponents of the distributed fuel controller 750 via the supply outlet724. In particular, the upstream air interface 722 (FIG. 3) and thedownstream air interface 723 (FIG. 3) are configured to be pneumaticallycoupled once a first frame unit 701 and a second frame unit 701 aredrawn together and coupled via the frame puller 709 (FIG. 3). Inaddition, the supply outlet 724 may include a plurality of air linesadapted to pneumatically couple with one or more components onboard thesplit fuel control module 700. For example, the supply outlet 724 mayinclude a manifold or other conventional flow divider and the associatedhardware and conduit to pneumatically couple with at least one of theprimary fuel shut-off valve 751, the secondary fuel shut-off valve 752,the main fuel control valve 753, a pilot fuel control valve 754, and atorch fuel control valve.

According to one embodiment the segmented air path 720 may include oneor more quick-release couplings. In particular, the air inlet 721, theupstream air interface 722, the downstream air interface 723, the supplyoutlet 724, and/or the gas vent may include a pneumatic coupling thatcan be coupled/decoupled without the use of tools. For example this mayinclude a detent/slide-collar coupling, a quarter turn coupling, or anyconventional coupling meeting the particular specifications of thepressurized gas/clean air supply and the instrument gas system of splitfuel control module 700.

The terminal box 730 is an enclosed junction where power enters theframe unit 701, and is routed to the various components onboard. Theterminal box 730 may include an enclosure, a power bus inside itsenclosure, and a standard power receptacle 731 (FIG. 2) accessible fromoutside its enclosure. Electrically-powered components of each frameunit 701 may be electrically coupled to the power bus. According to oneembodiment, the terminal box 730 may also receive and routecommunications lines. According to one embodiment, the terminal box 730may take an elongated shape, perpendicular to the centerline 702 of theframe unit 701, wherein its power receptacle 731 is located at an endaway from the centerline 702 and accessible from the side of the frameunit 701.

According to another embodiment, each frame unit 701 may include its ownterminal box 730. In particular, the electrically-powered components ofeach frame unit 701 may be electrically coupled to a local terminal box730. For example, each local terminal box 730 may include its own powersupply and be isolated from another frame unit 701, withoutframe-to-frame connections. Alternately, the first frame unit 701 mayreceive offboard power and then supply power to the second frame unit701.

According to one embodiment the terminal box 730 may be configured foruniversal installation. In particular, each terminal box may beconfigured as a local power supply for a single frame unit 701, andfurther configured to receive power from various supplies. For example,as above, all electrically-powered components of each frame unit 701 maybe electrically powered by a local terminal box 730, and the terminalbox 730 may include multiple power receptacles 731. According to oneembodiment, the terminal box 730 may include power receptacles 731 onopposite ends of the terminal box 730 such that a power plug may beengaged from either of the frame unit 701. In addition, the sameterminal box 730 may include an inboard power receptacle 731 (FIG. 2)configured to receive power from another terminal box 730. Wheremultiple frame unit 701 are used, a terminal box 730 may include twoinboard power receptacles 731, one configured to receive and oneconfigured to supply power in a daisy chain.

The transmitter 740 is a communication device that communicates feedbackregarding the split fuel control module 700. According to oneembodiment, the transmitter 740 may receive commands from a remotecontroller such as in control panel 107 (FIG. 1). As illustrated, thesplit fuel control module 700 may include multiple transmitters 740,relaying multiple measurements. According to one embodiment, themultiple transmitters 740 may include redundant or back-up transmitters740 that provide duplicative information.

Each transmitter 740 may include a component interface and a dataoutput. The component interface may include a communication link, asensor, or any combination thereof. The component interface isconfigured to receive measurements such as pressure, flow rates,state/state changes, etc. Likewise, the data output may include acommunication link, a data display, or any combination thereof. The dataoutput is configured to relay the received measurements to a remotecontroller or display (e.g., control panel 107) and/or to display thereceived measurements in situ. According to one embodiment, thetransmitter 740 may include a processor configured to convert thereceived measurements to a viewable or communicable format.

According to one embodiment, the transmitter 740 may be configured foruniversal installation as well. In particular, the transmitter 740 maybe configured to be installed with a plurality of gas turbine enginepackages 100 (FIG. 1), in a plurality of positions on a gas turbineengine package 100, and/or having a plurality of external interfaces.For example, where the transmitter 740 includes a viewable data display,it may be aligned with the centerline 702 of the base 703 (FIG. 2), suchthat the transmitter 740 is equally readable from either side of thecenterline 702. Alternately, the transmitter 740 may include duplicativedata displays, such that the transmitter 740 may be viewed, independentof which gas turbine engine package 100 installation and/orconfiguration it is used. Additionally, the transmitter 740 may includeduplicative data outputs, such that the transmitter 740 may be equallyaccessed, independent of which gas turbine engine package 100installation and/or configuration it is used.

INDUSTRIAL APPLICABILITY

The present disclosure generally applies to a split fuel control modulefor a gas turbine engine. The described embodiments are not limited touse in conjunction with a particular type of gas turbine engine or anytype of fuel. Gas turbine engines, and thus their components and supportsystems, may be suited for any number of industrial applications, suchas, but not limited to, various aspects of the oil and natural gasindustry (including include transmission, gathering, storage,withdrawal, and lifting of oil and natural gas), power generationindustry, aerospace and transportation industry, to name a few examples.

Generally, embodiments of the presently disclosed split fuel controlmodule are applicable to the use, operation, maintenance, repair, andimprovement of gas turbine engines, and may be used in order to improveperformance and efficiency, decrease maintenance and repair, and/orlower costs. In addition, embodiments of the presently disclosed splitfuel control module may be applicable at any stage of the gas turbineengine's life, from design to prototyping and first manufacture, andonward to end of life. Accordingly, the split fuel control module may beused in conjunction with a retrofit or enhancement to existing gasturbine engine, as a preventative measure, or even in response to anevent.

In particular, the presently disclosed split fuel control module mayprovide for increased fuel controller upgrades, economical retrofitting,and universal installation. As sufficient advancements become availablein fuel controller componentry to warrant and upgrade of the entiremodule, the disclosed split fuel control module provides for the upgradewithout having the added cost of first removing the gas turbine engineor the need to wait for a regularly scheduled engine removal. Instead,the split fuel control module may be installed with the gas turbineengine installed.

Moreover, by splitting the fuel control module for installation, aretrofit or upgrade may be easier and less cumbersome. In particular, byessentially splitting the fuel control module in two, it becomes easierto install into the gas turbine engine package. For example, being halfthe size, each half is lighter and more maneuverable to install. Also,lower cost lifting approaches may become an option. In addition, thesmaller size may include incidental benefits such as being able toreadily install each half though a single access port or doorway.

Also, the inclusion of features for universal installation may providethe additional benefits associated with having a single design andmultiple options for use in multiple installations and/or multipleconfigurations, which may have been customized to a unique gas turbineengine package or facility interfaces.

FIG. 6 is a flow chart of an exemplary method for installing a splitfuel control module. In particular, a gas turbine engine package 100 maybe modified, retrofitted, or manufactured as described above using thefollowing method, the above description, or a combination thereof. Asillustrated (and with reference to FIGS. 1-5), the gas turbine enginepackage 100 may be modified by installing the split fuel control module700.

The method begins with mechanically installing the split fuel controlmodule into the gas turbine engine package. In particular, the methodmay include installing a first frame unit into a gas turbine enginepackage 903, and installing a second frame unit into the gas turbineengine package proximate the first frame unit 904. These may bepredicated on the removal of any pre-existing fuel control system 901. Apre-existing fuel control system might be a “module” or could benon-modularized collection of components performing the same function.

Installing the first and second frame units 903, 904 may be furtherpredicated by fastening or installing a base plate to the gas turbineengine package 902. Where a base plate is used, installing the first andsecond frame units 903, 904 may include fastening the first frame unitto the base plate, and fastening the second frame unit to the baseplate. Also, installing the base plate to the gas turbine engine package902 may include attaching one or more additional support brackets to thebase plate and/or the support platform.

In addition, installation of the frame units may include a temporarypositioning of the first and second frame units, followed by asubsequent alignment and securing to the gas turbine engine packagedirectly or via the base plate. For example, the subsequent alignmentand securing may be performed after the first and second frame units arecoupled. Also for example, installation of the frame units may includevertically lowering the frame unit alongside the gas turbine engine tothe base plate, then sliding the frame unit into position to mount theframe unit to the base plate.

Once the first and second frame units are proximate each other, themethod may include drawing and coupling the first frame unit and thesecond frame unit together 906, According to one embodiment, drawing andcoupling the first frame unit and the second frame unit together 906 mayinclude aligning the first and second frame units with each other usingan interface alignment guide, and drawing them together using a framepuller, as discussed above. For example, one or more nuts may betightened on one or more threaded shafts while attached to each frameunit's inner side and while one or more taper pins are engaged to guidetheir travel.

The method further includes coupling a segmented fuel path broken acrosssegmented across a frame unit interface. In particular, the methodincludes coupling an upstream fuel interface with a downstream fuelinterface 908. For example, coupling the upstream fuel interface withthe downstream fuel interface 908 may include fluidly coupling matingflanges using a seal therebetween as discussed above. Alternately,coupling the upstream fuel interface with the downstream fuel interface908 may include fluidly coupling the segmented fuel path using anyconventional means.

The method may further include coupling a segmented air path brokenacross segmented across the frame unit interface. In particular, themethod may include coupling an upstream air interface with a downstreamair interface 910. For example, coupling the upstream air interface withthe downstream air interface 910 may include pneumatically couplingmating fittings using a quick-release coupling as discussed above.Alternately, coupling the upstream air interface with the downstream airinterface 910 may include pneumatically coupling the segmented air pathusing any conventional means.

The method further includes fluidly installing the split fuel controlmodule into the fuel system of gas turbine engine package 100. Inparticular, the method may include coupling a fuel inlet to a fuelsupply and a fuel outlet to a gas turbine fuel system 918. For example,coupling the fuel inlet to the fuel supply and the fuel outlet to thegas turbine fuel system 918 may include fluidly coupling mating flangesbetween fuel inlet and the fuel supply, and include fluidly couplingmating flanges between the fuel outlet and gas turbine fuel system, asdiscussed above. Alternately, coupling a fuel inlet to a fuel supply anda fuel outlet to a gas turbine fuel system 918 may include fluidlycoupling the split fuel control module using any conventional means.

According to one embodiment, the fuel outlet may include a plurality ofoutlets. For example the gas turbine fuel system may use independentfuel supplies for a main fuel system, a pilot fuel system, and/or torchfuel system. Accordingly, the fuel outlet may include separate matinginterfaces and be coupled to each independent system.

According to another embodiment, the split fuel control module mayrequire more than one segmented fuel path. In particular, the gasturbine engine may operate on various types of fuels, as discussedabove, and coupling the fuel inlet to the fuel supply and the fueloutlet to the gas turbine fuel system 918 may include fluidly coupling aplurality of fuel inlets and a plurality of fuel outlets, respectively.In addition, coupling the upstream fuel interface with the downstreamfuel interface 908 may include fluidly coupling a plurality of upstreamfuel interfaces with a plurality of downstream fuel interfaces. Forexample, where two fuels are sufficiently dissimilar, each may includeits own independent segmented fuel path.

The method may further include supplying pneumatic power to the splitfuel control module. In particular, the method may include coupling anair inlet of the segmented air path to an air supply, and an air outletof the segmented air path to a component of the distributed fuelcontroller 920. For example, coupling the air inlet of the segmented airpath to the air supply may include coupling the air inlet to an offboard instrument gas system using quick-release couplings. Also forexample, coupling the air outlet of the segmented air path to thecomponent of the distributed fuel controller may include coupling theair outlet to one or more air-powered and/or air-assisted fuel valvesusing quick-release couplings. Alternately, coupling the air inlet andthe air outlet of the segmented air path may include pneumaticallycoupling the segmented air path using any conventional means.

The method may further include supplying electrical power to the splitfuel control module. In particular, the method may include coupling apower supply to a terminal box 922. For example, coupling the powersupply to the terminal box 922 may include plugging in independent powersupplies to separate terminal boxes, one on each frame unit.Accordingly, where a first terminal box is mounted to the first frameunit and a second terminal box is mounted to the second frame unit,coupling the power supply to the terminal box 922 may include coupling asecond power supply to the second terminal box. Alternately, couplingthe power supply to the terminal box 922 may include electricallycoupling a single power supply to the first terminal box on the firstframe unit, and electrically coupling the first terminal box with thesecond terminal box using any conventional electrical couplings.

The method may further include communicably coupling the split fuelcontrol module with the fuel system of gas turbine engine package 100.In particular, the method may include establishing a communications linkbetween the split fuel control module and an external controller 924.For example, establishing a communications link between the split fuelcontrol module and an external controller 924 may include plugging awired communications link into the terminal box, wherein the terminalbox includes a communications bus or other communications router.Alternately, establishing a communications link between the split fuelcontrol module and an external controller 924 may include a wirelesscommunications link with the terminal box, wherein the terminal boxincludes a communications bus or other communications router. Also forexample, establishing a communications link between the split fuelcontrol module and an external controller 924 may include establishing adedicated communications link between an external controller and one ormore components onboard the split fuel control module.

The preceding detailed description is merely exemplary in nature and isnot intended to limit the invention or the application and uses of theinvention. The described embodiments are not limited to use inconjunction with a particular type of gas turbine engine. Hence,although the present embodiments are, for convenience of explanation,depicted and described as being implemented in a stationary gas turbineengine, it will be appreciated that it can be implemented in variousother types of gas turbine engines, and in various other systems andenvironments. Furthermore, there is no intention to be bound by anytheory presented in any preceding section. It is also understood thatthe illustrations may include exaggerated dimensions and graphicalrepresentation to better illustrate the referenced items shown, and arenot consider limiting unless expressly stated as such.

What is claimed is:
 1. A split fuel control module for a gas turbineengine, the split fuel control module comprising: a first frame unit,the first frame unit including a first base and a first inner side, thefirst inner side joined to and extending perpendicularly from the firstbase; a second frame unit, the second frame unit including a second baseand a second inner side, the second inner side joined to and extendingperpendicularly from the second base, the second inner side configuredto align and couple with the first inner side; a segmented fuel path,the segmented fuel path including a fuel inlet configured to receivefuel from a fuel supply, an upstream fuel interface, a downstream fuelinterface, and a fuel outlet configured to deliver fuel to the gasturbine engine, the upstream fuel interface fixed to the first frameunit, the downstream fuel interface fixed to the second frame unit andconfigured to mate with the upstream fuel interface when the first innerside is aligned and coupled to the second inner side; a distributed fuelcontroller, the distributed fuel controller including a primary fuelshut-off valve and a main fuel control valve, a first portion of thedistributed fuel controller fixed to the first frame unit and a secondportion of the distributed fuel controller fixed to the second frameunit.
 2. The split fuel control module of claim 1, wherein the firstframe unit, further includes a first outer side, the first outer sidelocated opposite the first base from the first inner side, the firstouter side joined to and extending perpendicularly from the first base;and wherein the second frame unit, further includes a second outer side,the second outer side located opposite the second base from the secondinner side, the second outer side joined to and extendingperpendicularly from the second base.
 3. The split fuel control moduleof claim 2, wherein the first frame unit and the second frame unit eachhave a center of gravity, respectively; wherein the first inner sideincludes a first plurality of inner side lifting devices, the firstplurality of inner side lifting devices located above the center ofgravity of the first frame unit; wherein the first outer side includes afirst plurality of outer side lifting devices, the first plurality ofouter side lifting devices located above the center of gravity of thefirst frame unit; wherein the second inner side includes a secondplurality of inner side lifting devices, the second plurality of innerside lifting devices located above the center of gravity of the secondframe unit; and wherein the second outer side includes a secondplurality of outer side lifting devices, the second plurality of outerside lifting devices located above the center of gravity of the secondframe unit.
 4. The split fuel control module of claim 3, wherein thefirst base is rectangular and includes a centerline, the centerlinenormal to both the first inner side and the first outer side; whereinthe first plurality of inner side lifting devices includes a first innerside lifting device located at a first perpendicular distance from thecenterline, and further includes a second inner side lifting devicelocated at a second perpendicular distance opposite the firstcenterline, the first perpendicular distance different from the secondperpendicular distance; and wherein the first outer plurality of liftingdevices includes a first outer side lifting device located at the firstperpendicular distance from the centerline, and further includes asecond outer side lifting device located at the second perpendiculardistance opposite the first centerline.
 5. The split fuel control moduleof claim 1, further comprising: a frame puller configured to drawtogether and couple the first frame unit and the second frame unit; andan interface alignment guide coupled to the first frame unit, theinterface alignment guide configured to guide the first frame unit andthe second frame unit into alignment over a range where the frame pullermay draw the first frame unit and the second frame unit together.
 6. Thesplit fuel control module of claim 5, wherein the frame puller includesa threaded shaft and a nut; and wherein the interface alignment guideincludes a taper pin.
 7. The split fuel control module of claim 1,wherein the frame puller is further configured to draw the upstream fuelinterface and the downstream fuel interface within 0.025″ of each other.8. The split fuel control module of claim 1, wherein the first base isrectangular and includes a centerline, the centerline normal to both thefirst inner side and the first outer side; wherein the first frame unitfurther includes a first side support configured structurally as acorner brace, the first side support coupled to and extendingorthogonally from the first base, the first inner side, and the firstouter side; and wherein the first frame unit further includes a secondside support configured structurally as a corner brace, the second sidesupport coupled to and extending orthogonally from the first base, thefirst inner side, and the first outer side, the second side supportopposite the centerline from the first side support.
 9. The split fuelcontrol module of claim 1, further comprising: a secondary fuel shut-offvalve; a pilot fuel control valve; and a segmented air path, thesegmented air path including an air inlet configured to receiveinstrument gas from an instrument gas supply, an upstream air interfacefixed to the first frame unit, a downstream air interface fixed to thesecond frame unit and detachably coupled to the upstream air interface,and a supply outlet configured to deliver fuel to at least one componentof the distributed fuel controller.
 10. The split fuel control module ofclaim 1, further comprising a terminal box, the terminal box includingan enclosure, a power bus inside the enclosure, and a power receptacleaccessible from outside the enclosure.
 11. A gas turbine engine packagecomprising: a gas turbine engine; a support platform; and the split fuelcontrol module of claim 1, the split fuel control module fluidly coupledto the gas turbine engine, and mounted to the support platform.
 12. Asplit fuel control module for a gas turbine engine, the split fuelcontrol module comprising: a first frame unit, the first frame unitincluding a first base and a first inner side, the first inner sidejoined to and extending perpendicularly from the first base; a secondframe unit, the second frame unit including a second base and a secondinner side, the second inner side joined to and extendingperpendicularly from the second base, the second inner side configuredto align and couple with the first inner side; a fuel inlet; a fueloutlet configured to deliver fuel to the gas turbine engine; an upstreamfuel interface fixed to the first frame unit; a downstream fuelinterface fixed to the second frame unit and detachably coupled to theupstream fuel interface; a primary fuel shut-off valve fixed to thefirst frame unit; and a main fuel control valve fixed to the secondframe unit.
 13. The split fuel control module of claim 12, wherein thefirst base is rectangular and includes a centerline, the centerlinenormal to both the first inner side and the first outer side; whereinthe first frame unit, further includes a first outer side, the firstouter side located opposite the first base from the first inner side,the first outer side joined to and extending perpendicularly from thefirst base; and wherein the first frame unit further includes a firstside support configured structurally as a corner brace, the first sidesupport coupled to and extending orthogonally from the first base, thefirst inner side, and the first outer side; and wherein the first frameunit further includes a second side support configured structurally as acorner brace, the second side support coupled to and extendingorthogonally from the first base, the first inner side, and the firstouter side, the second side support opposite the centerline from thefirst side support; and wherein the second frame unit, further includesa second outer side, the second outer side located opposite the secondbase from the second inner side, the second outer side joined to andextending perpendicularly from the second base.
 14. The split fuelcontrol module of claim 13, wherein the first frame unit and the secondframe unit each have a center of gravity, respectively; wherein thefirst inner side includes a first plurality of inner side liftingdevices, the first plurality of inner side lifting devices located abovethe center of gravity of the first frame unit; wherein the first outerside includes a first plurality of outer side lifting devices, the firstplurality of outer side lifting devices located above the center ofgravity of the first frame unit; wherein the second inner side includesa second plurality of inner side lifting devices, the second pluralityof inner side lifting devices located above the center of gravity of thesecond frame unit; and wherein the second outer side includes a secondplurality of outer side lifting devices, the second plurality of outerside lifting devices located above the center of gravity of the secondframe unit.
 15. The split fuel control module of claim 14, wherein thefirst base is rectangular and includes a centerline, the centerlinenormal to both the first inner side and the first outer side; whereinthe first plurality of inner side lifting devices includes a first innerside lifting device located at a first perpendicular distance from thecenterline, and further includes a second inner side lifting devicelocated at a second perpendicular distance opposite the firstcenterline, the first perpendicular distance different from the secondperpendicular distance; and wherein the first outer plurality of liftingdevices includes a first outer side lifting device located at the firstperpendicular distance from the centerline, and further includes asecond outer side lifting device located at the second perpendiculardistance opposite the first centerline.
 16. The split fuel controlmodule of claim 12, further comprising: a frame puller including athreaded shaft and a nut, the frame puller configured to draw togetherand couple the first frame unit and the second frame unit; and aninterface alignment guide including a taper pin, the interface alignmentguide configured to guide the first frame unit and the second frame unitinto alignment over a range where the frame puller may draw the firstframe unit and the second frame unit together.
 17. The split fuelcontrol module of claim 12, wherein the frame puller is furtherconfigured to draw the upstream fuel interface and the downstream fuelinterface within 0.025″ of each other.
 18. The split fuel control moduleof claim 12, further comprising: a secondary fuel shut-off valve; apilot fuel control valve; and a terminal box, the terminal box includingan enclosure, a power bus inside the enclosure, and a power receptacleaccessible from outside the enclosure.
 19. The split fuel control moduleof claim 12, further comprising a segmented air path, the segmented airpath including an air inlet configured to receive instrument gas from aninstrument gas supply, an upstream air interface fixed to the firstframe unit, a downstream air interface fixed to the second frame unitand detachably coupled to the upstream air interface, and a supplyoutlet configured to deliver fuel to at least one component of thedistributed fuel controller.
 20. The split fuel control module of claim12, further comprising a base plate; and wherein the first frame unitand the second frame unit are mounted to the base plate.